Turbine vane having improved flexibility

Abstract

Disclosed is a turbine vane having an airfoil in a cross section including a leading edge, a trailing edge, and a pressure surface and a suction surface connecting the leading edge and the trailing edge, the airfoil extending radially from a platform part to an end wall, wherein the trailing edge of the airfoil is provided with a cutback cut in a direction radially perpendicular to both the pressure surface and the suction surface.

The invention claimed is: 
     
       1. A turbine vane including an airfoil in a cross section, the airfoil comprising:
 a leading edge, a trailing edge, and a pressure surface and a suction surface connecting the leading edge and the trailing edge, the airfoil extending radially from a platform part of the turbine vane to an end wall of the turbine vane, 
 wherein the trailing edge of the airfoil is provided with one or more cutbacks in a direction radially perpendicular to both the pressure surface and the suction surface, 
 wherein a first cutback is located in proximity to the platform part of the turbine vane, 
 wherein a second cutback is located in proximity to the end wall of the turbine vane, 
 wherein the first cutback is located at a boundary of a fillet connecting the platform part of the turbine vane and the trailing edge of the airfoil, and 
 wherein the second cutback is located at a boundary of a fillet connecting the end wall of the turbine vane and the trailing edge of the airfoil. 
 
     
     
       2. The turbine vane of  claim 1 , wherein the first cutback or the second cutback is provided at a distal end thereof with an extended hole wider than a width of the first cutback or the second cutback. 
     
     
       3. The turbine vane of  claim 1 , further comprising:
 a plurality of cooling slots formed between the first cutback or the second cutback and at least one additional cutback formed along the trailing edge of the airfoil on the pressure surface side. 
 
     
     
       4. The turbine vane of  claim 2 , wherein the first cutback or the second cutback communicates with a cavity in the airfoil so that a cooling fluid is discharged through the first cutback or the second cutback. 
     
     
       5. A turbine vane assembly, comprising:
 a plurality of turbine vanes circumferentially coupled to an inner circumferential surface of a turbine housing, each turbine vane comprising an airfoil in a cross section including a leading edge, a trailing edge, and a pressure surface and a suction surface connecting the leading edge and the trailing edge, the airfoil extending radially from a platform part of the each turbine vane to an end wall of the each turbine vane, 
 wherein the trailing edge of the airfoil is provided with one or more cutbacks in a direction radially perpendicular to both the pressure surface and the suction surface, 
 wherein a first cutback is located in proximity to the platform part of the turbine vane, 
 wherein a second cutback is located in proximity to the end wall of the turbine vane, 
 wherein the first cutback is located at a boundary of a fillet connecting the platform part of the turbine vane and the trailing edge of the airfoil, and 
 wherein the second cutback is located at a boundary of a fillet connecting the end wall of the turbine vane and the trailing edge of the airfoil. 
 
     
     
       6. The turbine vane assembly of  claim 5 , wherein the first cutback or the second cutback is provided at a distal end thereof with an extended circular hole wider than a width of the first cutback or the second cutback. 
     
     
       7. The turbine vane assembly of  claim 6 , further comprising:
 a plurality of cooling slots formed between the first cutback or the second cutback and at least one additional cutback formed along the trailing edge of the airfoil on the pressure surface side. 
 
     
     
       8. The turbine vane assembly of  claim 6 , wherein the first cutback or the second cutback communicates with a cavity in the airfoil so that a cooling fluid is discharged through the first cutback or the second cutback. 
     
     
       9. A gas turbine, comprising:
 a combustor mixing fuel with compressed air to provide a fuel-air mixture and combusting the fuel-air mixture to generate an expanding high-temperature combustion gas; and 
 a turbine receiving the combustion gas generated in the combustor and converting a reaction force of the combustion gas to a rotary motion of a turbine blade, wherein the turbine comprises a plurality of turbine vanes guiding a flow of the combustion gas flowing to the turbine blade, each turbine vane having an airfoil in a cross section including a leading edge, a trailing edge, and a pressure surface and a suction surface connecting the leading edge and the trailing edge, the airfoil extending radially from a platform part of the each turbine vane to an end wall of the each turbine vane, 
 wherein the trailing edge of the airfoil is provided with one or more cutbacks in a direction radially perpendicular to both the pressure surface and the suction surface, 
 wherein a first cutback is located in proximity to the platform part of the turbine vane, 
 wherein a second cutback is located in proximity to the end wall of the turbine vane, 
 wherein the first cutback is located at a boundary of a fillet connecting the platform part of the turbine vane and the trailing edge of the airfoil, and 
 wherein the second cutback is located at a boundary of a fillet connecting the end wall of the turbine vane and the trailing edge of the airfoil. 
 
     
     
       10. The gas turbine of  claim 9 , wherein the first cutback or the second cutback is provided at a distal end thereof with an extended circular hole wider than a width of the first cutback or the second cutback. 
     
     
       11. The gas turbine of  claim 9 , further comprising:
 a plurality of cooling slots formed between the first cutback or the second cutback and at least one additional cutback formed along the trailing edge of the airfoil on the pressure surface side. 
 
     
     
       12. The gas turbine of  claim 10 , wherein the first cutback or the second cutback communicates with a cavity in the airfoil so that a cooling fluid is discharged through the first cutback or the second cutback.